An experimental dynamical systems approach to aeroelastic instabilities of swept wings
Abstract
Understanding and suppressing aeroelastic instabilities of aerodynamic flows is critical for stable operation of aircraft, improved handling capabilities and reduced danger of structural fatigue and failure. Our understanding of the nature and scaling of aeroelastic instabilities is still incomplete, particularly with regard to swept wing flows where tip vortices complete with cross flows associated with the wing sweep. Our approach will focus on making measurements in an expanded parameter space and mapping instability boundaries and flow physics over a wide range of flow and stiffness parameters, We will also characterize fluid damping over a wide range of geometries and flow conditions. Lastly we will employ machine learning tools to synthesize the large data sets that result from these experiments to extract meaningful low order dynamical model and connect these models with the complex flow features associated with the vortex flows over these complex geometries. The anticipated outcomes of this work will be improved understanding of the flow physics relating to aeroelastic instabilities and the development of better tools for measuring and modeling these systems. We expect that these developments will lead to improved designs for air vehicles. The research proposed in this project is Fundamental Research and has military and civilian applications.
Document Details
- Document Type
- DoD Grant Award
- Publication Date
- Jan 21, 2022
- Source ID
- FA95502110462XX0
Entities
People
- Kenneth S. Breuer
Organizations
- Air Force Office of Scientific Research
- Brown University
- United States Air Force